Compressor diffuser

ABSTRACT

A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to gas turbine compressordiffusers and, more particularly, to compressor diffusers with combustorsupports.

Current engine and rig test data on existing gas turbines shows thatflow energy losses within a compressor discharge case (CDC) at an axiallocation downstream from the compressor diffuser are an important factorin gas turbine efficiency and output. For new engine designs,traditional controls and apparatuses for mitigating these losses havebeen found to add length to the CDC. Unfortunately, these controlsincrease a complexity of the mechanical design of the gas turbine, as awhole, and add product costs to the gas turbine.

In addition, these controls and apparatuses may be combined with the useof multi-passage diffusers. However, the use of such multi-passagediffusers requires extensive casting and machining operations that alsoadd to the overall product costs.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect of the invention, a diffuser for a turbineengine, including an annular casing to seal compressor discharge air andstruts attached to the casing to delimit an annular array of intra-strutregions, is provided and includes a ring portion, including a ringshaped annular body with a forward face disposed on a forward sidethereof, the ring portion being supportable by one or more of thestruts, and a splitter portion, including a ring shaped annular bodywith an aft face disposed on an aft side thereof to mate with theforward face of the ring portion body, the splitter portion furtherincluding a lead edge, on a forward side of the splitter portion body,which is extendable into a flow path of the compressor discharge air tosplit the flow path into secondary flow paths defined radially outsideof and inside of the splitter portion body.

According to another aspect of the invention, a diffuser for a turbineengine, including an annular casing to seal compressor discharge air andstruts attached to the casing to delimit an annular array of intra-strutregions, is provided and includes a ring shaped annular body, which issupportable at an aft side thereof by one or more of the struts, thering shaped annular body including a lead edge, on a forward sidethereof, which is extendable into a flow path of the compressordischarge air to split the flow path into secondary flow paths definedradially outside of and inside of the ring shaped annular body and thelead edge.

According to yet another aspect of the invention, a diffuser for aturbine engine, including an annular casing to seal compressor dischargeair and struts attached to the casing to delimit an annular array ofintra-strut regions, is provided and includes a ring shaped annularbody, supportable at an aft side thereof by one or more of the struts,and including a lead edge, on a forward side of the annular body, whichis extendable into a flow path of the compressor discharge air to splitthe flow path into secondary flow paths defined radially outside of andinside of the ring shaped annular body and the lead edge, and asupporting assembly, disposed on the ring shaped annular body within anintra-strut region, and on which a combustor assembly is supportable.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter, which is regarded as the invention, is particularlypointed out and distinctly claimed in the claims at the conclusion ofthe specification. The foregoing and other features, and advantages ofthe invention are apparent from the following detailed description takenin conjunction with the accompanying drawings in which:

FIG. 1 is a rear perspective view of a compressor discharge casing and adiffuser in accordance with embodiments;

FIG. 2 is forward perspective view of a compressor discharge casing anda diffuser in accordance with embodiments;

FIG. 3 is a side sectional view of the diffuser annular body of FIGS. 1and 2;

FIG. 4 is a perspective view of a splitter portion of the diffuser ofFIGS. 1-3;

FIG. 5 is a rear perspective view of a compressor discharge casing, adiffuser and supporting assemblies in accordance with embodiments; and

FIG. 6 is a side sectional view of a compressor discharge casing, adiffuser and a combustor assembly supported on the diffuser inaccordance with embodiments.

The detailed description explains embodiments of the invention, togetherwith advantages and features, by way of example with reference to thedrawings.

DETAILED DESCRIPTION OF THE INVENTION

With reference to FIGS. 1-6, a diffuser 10 is provided for use in aturbine engine 1. The turbine engine 1 may include a rotor that rotatesabout a centerline thereof, a compressor section upstream of thediffuser 10, which compresses inlet air and discharges hot compressordischarge air, an annular compressor discharge casing (CDC) 20, whichseals the compressor discharge air from the rotor and a set of struts30, and which includes wall surfaces 21 and 22 that delimit a regionthrough which the hot compressor discharge air is able to flow.

With reference to FIGS. 1 and 2, each of the struts 30 includes opposingforward and aft ends. The ends are each attached to the CDC 20 such thateach of the struts 30 is substantially aligned with a longitudinal axisof the rotor and with the struts disposed at substantially regularlyspaced circumferential locations. In this way, the struts 30 delimit anannular array of intra-strut regions 40. A can-annular array ofcombustor assemblies 110, which are receptive of the compressordischarge air for combustion operations, may be supported on portions ofthe diffuser 10 in these intra-strut regions 40, as will be describedbelow.

With reference to FIG. 3, the diffuser 10 includes the wall surfaces 21and 22, a ring portion 50 and a splitter portion 60. The ring portion 50includes a ring shaped annular body 51 and forward and aft faces 53 and52, which are disposed on opposing forward and aft facing sides of theannular body 51, respectively. The ring portion 50 is supportable by oneor more of the struts 30. Support for the ring portion 50 may begenerally provided by way of a connection between the strut 30 and theaft face 52, although other components of the ring portion 50 may alsohave connections to the strut 30.

With reference to FIG. 4, the splitter portion 60 includes a ring shapedannular body 61 and an aft face 62, which is disposed on an aft surfaceof the splitter portion body 61. The aft face 62 of the splitter portion60 may be mated with the forward face 53 of the ring portion such thatthe ring and splitter portions 50 and 60 cooperatively form a singularring-shaped structure.

The splitter portion 60 further includes a lead edge 70. The lead edge70 is formed at an intersection of first and second forward faces 71 and72 of the splitter portion body 61. The faces 71 and 72 are taperedtoward one another in the upstream flow direction. With the ring portion50 supported by the struts 30, the lead edge 70 is extendable into aflow path 80 of the compressor discharge air. The diffuser 10 is therebyconfigured to split the flow path 80 into secondary flow paths 81 and82, which are defined radially outside of and inside of the diffuser 10and between faces 71 and 72 and wall surfaces 21 and 22, respectively.That is, the secondary flow paths 81 and 82 are at least initiallyradially divergent while they may terminate downstream at combustorassemblies 110 to be described below.

The diffuser 10 may be provided as a single component or as multiplediffusers 10 that are each structured substantially as described above.Where the diffuser 10 is provided as multiple diffusers 10, eachindividual diffuser 10 is independently supported on at least oneindividual strut 30. Of course, it is to be understood that still otherconfigurations for the diffuser 10 are possible and that, for example,each individual diffuser 10 may be supported on two or more struts 30.Where the diffuser 10 is formed of multiple components, such as upperportion 65 and lower portion 66, the components may be conjoined bybolts 67 at joint(s) therein. Seals or baffles to prevent or control airleakage between the components may also be employed.

The ring portion 50 is integrally coupled to the struts 30. That is, thering portion 50 may be cast or otherwise suitably formed along with thestruts 30 and the CDC 20. The splitter portion 60, on the other hand,may be formed by a separate machining process and later mated with thering portion 50. As such, the faces 71 and 72, which are to besubstantially smooth, can be machined with a high degree of precision.With this said, it is understood that the splitter portion 60 may beformed integrally with the ring portion 50, the struts 30 and the CDC 20as long as processing tolerances can be maintained with a high degree ofprecision, and as long as mechanical stresses are acceptable. Once thesplitter portion 60 and the ring portion 50 are formed, the splitterportion 60 is coupled to the ring portion 50. Mechanical connectors,such as axial bolts 90 or some other type of suitable fastening element,may serve to provide for this coupling.

With reference to FIG. 5, the diffuser 10, with the constructiondescribed above, is supported on one or more of the struts 30 and splitsthe flow path 80 of the compressor discharge air. In an additionalconfiguration, combustor assemblies 110 are supported by at least one ofthe ring portion 50 and the splitter portion 60 of the diffuser 10 in acan-annular array of combustor assemblies 110. Here, each individualcombustor assembly 110 is supported on a radially outward portion of atleast one of the ring portion 50 and the splitter portion 60 and withinan intra-strut region 40.

With reference to FIG. 6, a supporting assembly 100 provides for thesupport of each combustor assembly 110. The supporting assembly 100includes a pad 101 and a bracket 102. The pad 101 is coupled to at leastone of the ring portion 50 and the splitter portion 60. The bracket 102is coupled to the pad 101 and may be bullhorn-shaped. In this way, thebracket 102 may include lateral wings along which sliding attachmentsfor attachment to the combustor assembly 110 are disposed. Here, thesliding attachments maintain the support for the combustor assembly 110during thermal expansion or contraction.

While the invention has been described in detail in connection with onlya limited number of embodiments, it should be readily understood thatthe invention is not limited to such disclosed embodiments. Rather, theinvention can be modified to incorporate any number of variations,alterations, substitutions or equivalent arrangements not heretoforedescribed, but which are commensurate with the spirit and scope of theinvention. Additionally, while various embodiments of the invention havebeen described, it is to be understood that aspects of the invention mayinclude only some of the described embodiments. Accordingly, theinvention is not to be seen as limited by the foregoing description, butis only limited by the scope of the appended claims.

The invention claimed is:
 1. A diffuser for a turbine engine, includingan annular casing to seal compressor discharge air and struts attachedto the casing to delimit an annular array of intra-strut regions, thediffuser comprising: a ring portion, including a ring shaped annularbody with a forward face disposed on a forward facing side thereof andan aft face disposed on an aft facing side thereof, the forward and aftfacing sides opposing one another and the ring portion being supportableby an integral connection between one or more of the struts and the aftface; and a splitter portion, including a ring shaped annular body withan aft face disposed on an aft side thereof to mate with the forwardface of the ring portion body, the splitter portion further including: alead edge, on a forward side of the splitter portion body, which isextendable into a flow path of the compressor discharge air to split theflow path into secondary flow paths defined radially outside of andinside of the splitter portion body.
 2. The diffuser according to claim1, wherein at least one of the ring portion and the splitter portion isformed of plural segments.
 3. The diffuser according to claim 1, whereinthe ring portion is integrally coupled to the struts.
 4. The diffuseraccording to claim 1, wherein the splitter portion is coupled to thering portion.
 5. The diffuser according to claim 1, wherein the splitterportion is mechanically connected to the ring portion.
 6. The diffuseraccording to claim 1, wherein the splitter portion comprises upper andlower portions.
 7. The diffuser according to claim 6, further comprisingmechanical connectors to conjoin the upper and lower portions.
 8. Thediffuser according to claim 1, further comprising a supporting assemblyon which a combustor assembly is supportable.
 9. The diffuser accordingto claim 8, wherein the supporting assembly is disposed on at least oneof the ring portion and the splitter portion within an intra-strutregion.
 10. The diffuser according to claim 8, wherein the supportingassembly comprises a pad coupled to the at least one of the ring portionand the splitter portion.
 11. The diffuser according to claim 1, whereinthe lead edge comprises substantially smooth faces tapered toward oneanother in a radial direction.
 12. A diffuser for a turbine engine,including an annular casing to seal compressor discharge air and strutsattached to the casing to delimit an annular array of intra-strutregions, the diffuser comprising: a ring shaped annular body having anaft face at an aft facing side thereof, which is supportable by anintegral connection between one or more of the struts and the aft face,the ring shaped annular body including: a lead edge, on a forward facingside thereof, which is opposed to the aft facing side and is extendableinto a flow path of the compressor discharge air to split the flow pathinto secondary flow paths defined radially outside of and inside of thering shaped annular body and the lead edge.
 13. The diffuser accordingto claim 12, further comprising a supporting assembly, disposed on thering shaped annular body within an intra-strut region, and on which acombustor assembly is supportable.
 14. The diffuser according to claim13, wherein the supporting assembly comprises a pad coupled to the ringshaped annular body.
 15. A turbine engine comprising the diffuser ofclaim 13, a compressor to discharge the compressor discharge air and thecombustor assembly, which is receptive of the compressor discharge airfrom the secondary flow paths, and which is supported on the supportingassembly.
 16. The turbine engine according to claim 15, wherein thediffuser is plural in number.
 17. A turbine engine comprising thediffuser of claim 12, a compressor to discharge the compressor dischargeair and a combustor assembly, which is receptive of the compressordischarge air from the secondary flow paths.
 18. The turbine engineaccording to claim 17, wherein the diffuser is plural in number, withthe plural diffusers disposed in parallel with one another.
 19. Adiffuser for a turbine engine, including an annular casing to sealcompressor discharge air and struts attached to the casing to delimit anannular array of intra-strut regions, the diffuser comprising: a ringshaped annular body having an aft face at an aft facing side thereof,supportable an integral connection between one or more of the struts andthe aft face, and including a lead edge, on a forward facing sidethereof, which is opposed to the aft facing side and is extendable intoa flow path of the compressor discharge air to split the flow path intosecondary flow paths defined radially outside of and inside of the ringshaped annular body and the lead edge; and a supporting assembly,disposed on the ring shaped annular body within an intra-strut region,and on which a combustor assembly is supportable.
 20. The diffuseraccording to claim 19, wherein the supporting assembly comprises a padcoupled to the at least one of the ring portion and the splitterportion.